Vortex structuring of the gas flow in the compressor cascade

Aerospace propulsion engineering


Shcherbakov M. A.1*, Marchukov E. Y.2**, Kartovitskiy L. L.2***

1. Development Design Bureau named after A.M. Lyulka, 13, Kasatkina str., Moscow, 129301, Russia
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: sherbakovma@mail.ru
**e-mail: kaf205@mail.ru
***e-mail: levka_58@mail.ru


In this paper, the numerical study results for spherical cavities on the suction face of the compressor blade have been done to define the range of the compressor cascade operating condition without the flow separation. For increase of the regime without the flow separetion the range of optimal geometric parameters of cavities were obtaned. The modified blade profile characteristic was compared with the basic profile on the other compressor cascade operatinfg conditions. It is shown the designate study field has future.


turbulent model, CFD, compressor cascade, vortex structure


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